曝光臺 注意防騙 網曝天貓店富美金盛家居專營店坑蒙拐騙欺詐消費者

indicates the direction to roll the aircraft to return to wings level.
Roll
Command
Excessive
Attitude
Sphere
GF1110_099
FLIGHT INSTRUMENTS
REV 51, Aug 14, 2006 Flight Crew Operating Manual
CSP 700−6
Volume 2
11−10−99
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED)
General
The EVS consists of cockpit controls, a Head−Up Display (HUD) System, an Infrared Sensor
System (ISS) and FMS CDU. The ISS consists of an Infrared Sensor Unit (ISU) and an Infrared
Window (IRW).
The EVS imagery can significantly improve the pilot’s capability to detect approach lights and
visual references of the runway environment that may not otherwise be visible under poor visibility
conditions. The EVS also provides enhanced situational awareness during night operations.
The EVS enable descent and operation below decision altitude (DA) based on the pilot’s
observation of the EVS image.
EVS Overview
The EVS is composed of two sub systems,
1. The Head−Up Display (HUD) System, which is comprised of the following units:
• Head−Up Display Computer (HUD Computer)
• Computer Mounting Tray
• Optical Projector Unit (OPU)
• Combiner Optical Unit (COU)
• Mounting Tray (MTR)
• Sun Visor
• Cockpit Controls
2. The Infrared Sensor System (ISS), which is comprised of the following units:
• Infrared Sensor Unit (ISU)
• Infrared Window (IRW)
The Infrared Sensor Unit (ISU) is mounted inside the aircraft TRU bay, aft of the radome. The ISU
provides a monochrome video image in RS170 standard to the HUD Computer and FMS CDU.
The Infrared Window (IRW) consists of sapphire glass mounted in an EVS heated fairing. The IRW
has a heating element to protect against ice build up from the outside environment, and to prevent
condensation from the inside of the TRU bay. The EVS Heater Controller (EVSHC) controls the
IRW and fairing heating.
The IRW allows the ISU to see the forward scene of the aircraft, while protecting the ISU from the
outside environment.
The HUD displays the IR image via the projector onto the combiner and generates the raster
symbology that overlays the IR image. When the EVS image clear switch is selected to CLR or
EVS is turned off, the HUD operates in the basic HUD mode.
The HUD interfaces with the ISU and the aircraft systems through ARINC 429 buses and discrete
signals. All communication between the EVS and the aircraft systems are conducted via the HUD
computer.
The EVS controls are located with those for the HUD on the aircraft glare shield panel.
FLIGHT INSTRUMENTS
Flight Crew Operating Manual REV 51, Aug 14, 2006
CSP 700−6
Volume 2
11−10−100
ENHANCED VISION SYSTEM (EVS) (IF INSTALLED) (CONT'D)
EVS Architecture
GF1110_112
HFPC
HFDS Brightness
Projector and Combiner Tray
IAC
FDR
FMS CDU
EVS Brightness
HFDS On S/W
EVS On S/W
NUC S/W
EVS System
Raster
Image
Clear S/W
Contrast
Brightness
Windows
Temp
Sensor Image
RS−170
EVS Control
ARINC 429
EVS Status
Sensor Image RS−170
28 VDC Bus
115 VAC Bus
EVS Data
ARINC 429
Video Processing
Module
Hand Wheel
Pilot’s
EVS Clear Switch
EVS HUD Controls
Projector
Optical
Unit
Projector
Optical
Unit
(DAU) Symbology
AVIONICS
HFPC Tray Modified Fan
IR Sensor
Unit
IPS
IR Window
Unit
Legend
Existing Signal
New or modified
signal or data
Existing EVS
components
New EVS
components
Other
sub−system
MSK Board and
Ancillary H/W
EVS Ice Protection System Overview
The EVS Ice Protection System (EVS IPS) is comprised of the following units:
• EVS Heater Controller (EVSHC)
• EVS Heated Fairing (EVSHF)
• Infrared Window (IRW)
The EVSHC is located in the nose TRU bay and provides regulation and control of AC current to
the EVS Heated Fairing and Infrared Window.
The power distribution of the EVSHC is controlled using zero-crossed Heater Power Switches
(HPS) and redundant Fail Safe Relays. To ensure adequate power is distributed to the heater
mats, the controller performs current monitoring and is able to detect both over and undercurrent
faults.
Temperature sensors for control and monitoring are kept in separate channels for redundancy and
the controller can utilize a single sensor to perform both functions in case of failure. This degraded
　
中國航空網 www.k6050.com
航空翻譯 www.aviation.cn
本文鏈接地址：龐巴迪挑戰者手冊7(11)